Composite Panel Power System

ABSTRACT

An embodiment of the present disclosure provides a method and apparatus for supplying an electrical current. The method comprises sending the electrical current into a device from a panel comprising a dielectric core. Further, the method comprises a first sheet with a first conductive adhesive attaching the first sheet to a first side of the dielectric core, wherein the first conductive adhesive is a first electrode for a battery. Yet further, the method comprises a second sheet with a second conductive adhesive attaching the second sheet to a second side of the dielectric core, wherein the second conductive adhesive is a second electrode for the battery. Still further, the method comprises operating the device using the electrical current from the battery in the panel.

This application is a continuation of U.S. patent application Ser. No.15/014,381, filed Feb. 3, 2016, now U.S. Pat. No. 10,414,358, which isincorporated by reference herein in its entirety.

BACKGROUND INFORMATION 1. Field:

The present disclosure relates generally to aircraft and, in particular,to power systems in aircraft. Still more particularly, the presentdisclosure relates to a method and apparatus for a battery in acomposite panel for an aircraft.

2. Background:

Aircraft are being designed and manufactured with greater and greaterpercentages of lighter weight materials. For example, panels arecommonly used in the interiors of aircraft. Panels may be used to formwalls, ceilings, floors, closets, doors, and other structures in anaircraft.

The panels used in aircraft are often composite panels. For example, acomposite panel may be a sandwich composite panel. The basic structureis comprised of three main layers: a core between two relatively thinouter layers. The core typically has a low density, such as a honeycombcore. The outer layers are typically a pre-impregnated resin fiberweave.

This type of structure is able to receive shear loads while the outerlayers may receive in-plane stresses in a desired manner. As a result,these types of composite panels may have a high bending stiffness with alower density and weight as compared to other types of composite panels.

Further, decorative laminates are often placed on composite panels usedfor walls in the interior of the aircraft to provide aesthetics,information or directions, or some combination thereof. With theincreasing use of organic light emitting diode (OLED) displays, thesedisplays may also be attached to the composite panels.

Additionally, the composite panels also may be used in structures, suchas stowage bins, cabinets, and doors. Further devices, such as lights,electromechanical locks, and other devices, may be formed in thecomposite panels.

With the number of different devices that use electrical power, atechnical problem is present with providing power to the increasednumber of devices in an aircraft. The increased use of these devices inthe interior of an aircraft increases the power use in the aircraft. Insupplying power to these devices, power lines are used to connect thedevices in the aircraft's power system.

For example, if each storage bin in an aircraft has an electromechanicallatch, providing power to operate these latches increases the number ofwires needed in the aircraft. As another example, if organic lightemitting diode displays are used on composite panels for the walls,ceilings, doorways, or other locations, wires are used to connect theseorganic light emitting diode displays to the power system in theaircraft.

Thus, as the number of devices associated with composite panelsincreases, the amount of power and the complexity of supplying power tothese devices increase. Additionally, the weight of the aircraftincreases with the increased use of these devices and wiring systemsneeded to connect the devices to power systems.

Providing power to these devices may be more difficult and costly thandesired. For example, the use of wires to connect devices to powersystems adds to the cost and the weight of the aircraft. Further, thewires also increase the time and complexity in assembling the aircraft,resulting in increased production time and costs to manufacture theaircraft. Additionally, the amount of power that can be supplied fromthe power systems in the aircraft is limited. As a result, a largerauxiliary power unit, an additional auxiliary power unit, additionalbatteries, or other types of power supplies may be needed in theaircraft, which also increase the weight and the cost of the aircraft.

Therefore, it would be desirable to have a method and apparatus thattake into account at least some of the issues discussed above, as wellas other possible issues. For example, it would be desirable to have amethod and apparatus that overcome a technical problem with providingpower to devices associated with composite panels in an aircraft.

SUMMARY

An embodiment of the present disclosure provides an apparatus. Theapparatus comprises a dielectric core; a first sheet with a firstconductive adhesive attaching the first sheet to a first side of thedielectric core, wherein the first conductive adhesive is a firstelectrode for a battery; and a second sheet with a second conductiveadhesive attaching the second sheet to a second side of the dielectriccore, wherein the second conductive adhesive is a second electrode forthe battery, wherein the dielectric core, the first sheet, and thesecond sheet form a panel.

Another embodiment of the present disclosure provides a method forsupplying an electrical current. The method comprises sending theelectrical current into a device from a panel comprising a dielectriccore. Further, the method comprises a first sheet with a firstconductive adhesive attaching the first sheet to a first side of thedielectric core, wherein the first conductive adhesive is a firstelectrode for a battery. Yet further, the method comprises a secondsheet with a second conductive adhesive attaching the second sheet to asecond side of the dielectric core, wherein the second conductiveadhesive is a second electrode for the battery. Still further, themethod comprises operating the device using the electrical current fromthe battery in the panel.

Yet another embodiment of the present disclosure provides an aircraftpanel. The aircraft panel comprises a honeycomb core that has dielectricproperties. Further, the aircraft panel comprises a first sheet with afirst conductive adhesive attaching the first sheet to a first side ofthe honeycomb core, wherein the first conductive adhesive is a firstelectrode for a battery. Yet further, the aircraft panel comprises asecond sheet with a second conductive adhesive attaching the secondsheet to a second side of the honeycomb core, wherein the secondconductive adhesive is a second electrode for the battery, wherein thebattery is part of a composite panel.

The features and functions can be achieved independently in variousembodiments of the present disclosure or may be combined in yet otherembodiments in which further details can be seen with reference to thefollowing description and drawings.

BRIEF DESCRIPTION OF THE DRAWINGS

The novel features believed characteristic of the illustrativeembodiments are set forth in the appended claims. The illustrativeembodiments, however, as well as a preferred mode of use, furtherobjectives and features thereof, will best be understood by reference tothe following detailed description of an illustrative embodiment of thepresent disclosure when read in conjunction with the accompanyingdrawings, wherein:

FIG. 1 is a pictorial illustration of an aircraft in accordance with anillustrative embodiment;

FIG. 2 is an illustration of a block diagram of a battery environment inaccordance with an illustrative embodiment;

FIG. 3 is an illustration of a block diagram of a panel in accordancewith an illustrative embodiment;

FIG. 4 is an illustration of a panel in accordance with an illustrativeembodiment;

FIG. 5 is an illustration of a panel with a device in accordance with anillustrative embodiment;

FIG. 6 is an illustration of a cross-sectional view of a panel with adevice in accordance with an illustrative embodiment;

FIG. 7 is an illustration of a composite panel used in a wall in anaircraft in accordance with an illustrative embodiment;

FIG. 8 is an illustration of a composite panel used in a storage in anaircraft in accordance with an illustrative embodiment;

FIG. 9 is an illustration of a composite panel used in a wall in anaircraft in accordance with an illustrative embodiment;

FIG. 10 is an illustration of a flowchart of a process for supplyingelectrical current to a device in accordance with an illustrativeembodiment;

FIG. 11 is an illustration of a block diagram of an aircraftmanufacturing and service method in accordance with an illustrativeembodiment; and

FIG. 12 is an illustration of a block diagram of an aircraft in which anillustrative embodiment may be implemented.

DETAILED DESCRIPTION

The illustrative embodiments recognize and take into account one or moredifferent considerations. The illustrative embodiments recognize andtake into account that providing power to devices associated with panelsmay be more difficult than desired.

The illustrative embodiments recognize and take into account thatsupplying power to a device, such as an organic light emitting diodedisplay, currently involves running wires through a panel or panels froma power system to the organic light emitting diode display. The powersystem may be, for example, an auxiliary power supply or a battery inanother location in an aircraft.

The illustrative embodiments recognize and take into account thatrunning wires to and through panels may not provide a desired solution.The illustrative embodiments recognize and take into account thatrunning wires through the panel involves cutting channels in the core.Placing the wires in the channels and then filling the channels withepoxy or a potting material adds to the complexity of manufacturing thepanel. The outer layers may then be bonded to the core. The illustrativeembodiments recognize and take into account that this solution requiresadditional time to manufacture the panel.

Further, the illustrative embodiments also recognize and take intoaccount that this solution also increases the weight of the aircraft.The use of wires, a potting material, and other materials, in additionto those used for the panel, increases the weight of the panel, which inturn increases the weight of the aircraft.

Thus, the illustrative embodiments provide a method and apparatus tosupply power to devices associated with panels. In one illustrativeexample, a panel comprises a dielectric core, a first sheet with a firstconductive adhesive, and a second sheet with a second conductiveadhesive. The first sheet with the first conductive adhesive attachesthe first sheet to a first side of the dielectric core. The firstconductive adhesive is a first electrode for a battery. The second sheetwith the second conductive adhesive attaches the second sheet to asecond side of the dielectric core. The second conductive adhesive is asecond electrode for the battery. The dielectric core, the first sheetwith the first adhesive, and the second sheet with the second adhesiveform a panel.

With reference now to the figures and, in particular, with reference toFIG. 1, a pictorial illustration of an aircraft is depicted inaccordance with an illustrative embodiment. In this example, aircraft100 has wing 102 and wing 104 attached to fuselage 106. Aircraft 100also includes engine 108 attached to wing 102 and engine 110 attached towing 104.

Fuselage 106 has aft section 112. Aft section 112 is the tail section offuselage 106 in this illustrative example. Horizontal stabilizer 114,horizontal stabilizer 116, and vertical stabilizer 118 are attached toaft section 112 of fuselage 106.

Fuselage 106 also has cockpit 120 and passenger cabin 122. In thisexample, passenger cabin 122 may include passenger seating in seatingarea 124. Seating area 124 may include a number of aircraft seats. Asused herein, “a number of” items means one or more items. For example,“a number of aircraft seats” means one or more aircraft seats.

Further, seating area 124 in passenger cabin 122 also includes storageareas, such as a number of overhead compartments in the form of stowagebins 125. In this illustrative example, passenger cabin 122 also mayinclude lavatory 126.

As depicted in this figure, seating area 124 is divided into first-classseating 132, business class seating 134, and economy seating 136. Theseareas may be separated from each other by partitioning structures in theform of bulkhead 138, bulkhead 140, and bulkhead 142. In this particularexample, bulkhead 142 divides economy seating 136 in seating area 124.

Composite panels may be used in various locations within aircraft 100.For example, composite panels may be used for walls 144 for lavatory126. Door 146 also may be formed using composite panels. Bulkhead 138,bulkhead 140, and bulkhead 142 may be formed using composite panels. Asanother example, stowage bins 125 include composite panels.

In the illustrative example, one or more of the different compositepanels may include a number of batteries. These batteries are formed aspart of the composite panels for one or more of these different interiorcomponents in aircraft 100. The batteries may be used to power linereplaceable units that are associated with the composite panels.

When one component is “associated” with another component, theassociation is a physical association. For example, a first component,such as a line replaceable unit, may be considered to be physicallyassociated with a second component, such as a composite panel, by atleast one of being secured to the second component, bonded to the secondcomponent, mounted to the second component, welded to the secondcomponent, fastened to the second component, or connected to the secondcomponent in some other suitable manner. The first component also may beconnected to the second component using a third component. The firstcomponent may also be considered to be physically associated with thesecond component by being formed as part of the second component, anextension of the second component, or both.

With reference next to FIG. 2, an illustration of a block diagram of abattery environment is depicted in accordance with an illustrativeembodiment. In this illustrative example, battery environment 200includes platform 202. In this illustrative example, platform 202 takesthe form of aircraft 204. Aircraft 100 in FIG. 1 is an example of oneimplementation of aircraft 204.

As depicted, platform 202 is comprised of parts 206. Parts 206 may takevarious forms. For example, parts 206 may be selected from at least oneof a wall, a door, a partition, a bulkhead, a floor, a ceiling, acloset, a lavatory, a cabinet, a stowage bin, or some other suitabletype of part.

As used herein, the phrase “at least one of”, when used with a list ofitems, means different combinations of one or more of the listed itemsmay be used, and only one of each item in the list may be needed. Inother words, “at least one of” means any combination of items and numberof items may be used from the list, but not all of the items in the listare required. The item may be a particular object, thing, or category.

For example, without limitation, “at least one of item A, item B, oritem C” may include item A, item A and item B, or item B. This examplealso may include item A, item B, and item C or item B and item C. Ofcourse, any combinations of these items may be present. In someillustrative examples, “at least one of” may be, for example, withoutlimitation, two of item A; one of item B; and ten of item C; four ofitem B and seven of item C; or other suitable combinations.

In the illustrative example, parts 206 include panels 207. Panels 207may take the form of composite panels 208. Composite panels 208 includea number of layers that are formed from a composite material.

In the illustrative example, the composite material is a reinforcedplastic, such as a fiber reinforced polymer. In other words, fibers inwhich a resin is present. For example, fibers may include at least oneof fiberglass, carbon fiber, para-aramid synthetic fibers, or othersuitable types of fibers. These fibers may be woven into a fabric. Theresin may be, for example, a polymer resin, a shape memory polymerresin, or some other suitable type of resin that provides desiredproperties for composite panels 208.

In the illustrative example, panel 210 in panels 207 may form a part inparts 206. For example, panel 210 may form at least part of a structurein parts 206 selected from one of an interior wall, a ceiling, anoverhead stowage bin, a door, a closet, a sidewall, a partition, afloor, or some other suitable structure.

As depicted, panel 210 in panels 207 includes dielectric core 212, firstsheet 214, and second sheet 216. In these illustrative examples, firstsheet 214 and second sheet 216 are attached to dielectric core 212. Inthis illustrative example, when composite materials are used to form atleast one of first sheet 214 or second sheet 216, panel 210 takes theform of composite panel 218.

Further, first sheet 214 has first conductive adhesive 220 attachingfirst sheet 214 to first side 236 of dielectric core 212. Firstconductive adhesive 220 forms first electrode 222 for battery 224.Second sheet 216 has second conductive adhesive 226 attaching secondsheet 216 to second side 238 of dielectric core 212. Second conductiveadhesive 226 forms second electrode 228 for battery 224. In thisillustrative example, dielectric core 212 forms dielectric insulator 230for battery 224.

In this manner, first conductive adhesive 220, second conductiveadhesive 226, and dielectric core 212 form battery 224. As depicted,battery 224 is integrated as part of panel 210. Further, the formationof battery 224 does not require additional components that may addundesired weight or bulk to panel 210. For example, wires, pottingmaterial, and other materials that may be needed to run wires may beavoided.

As depicted, a conductive adhesive is used in place of a normal adhesivetypically used in panels. An adhesive is any material that binds twoobjects together and resists separation of the two objects from eachother. The adhesive may be comprised of a material that binds or adheresobjects together that are of a different or same make-up and developsstrength along the joined surfaces of the objects. The adhesive may beselected from one of glue, epoxy, cement, mucilage, paste, or some othersuitable material.

A conductive adhesive is any adhesive that contains conductive materialwithin the adhesive. The conductive material may be suspended, orotherwise contained, within the adhesive. The conductive material may beselected from at least one of a metal, an alloy, silver, copper, gold, asemi-metal, or graphite/carbon. The conductive material may have a formselected from at least one of nano-particles, fibers, granules, strands,nodules, filaments, or other suitable forms.

The composition of conductive materials used in first conductiveadhesive 220 and second conductive adhesive 226 may depend on variousfactors. For example, if resistance to corrosion is desired, thematerial for the conductive adhesive may be based on that factor.

For example, gold may be used when resistivity to corrosion is desired.For efficiency, silver may be used. For cost, copper may be selected. Ina similar fashion, the shape of the conductive materials is alsoselected based on various factors, such as cost, thickness of theadhesive layer, or other suitable factors.

In the illustrative example, device 232 may be electrically connected tobattery 224. In particular, device 232 may be electrically connected tofirst electrode 222 and second electrode 228. This connection allowselectrical current 240 to flow between device 232 and battery 224 in amanner that supplies power to allow device 232 to operate.

The electrical connection is direct or indirect. For example, device 232may be directly connected to battery 224 through conductive lines. Inother illustrative examples, device 232 may be connected to battery 224through at least one of an amplifier, a switch, a diode, or some othersuitable component.

As depicted, device 232 may take various forms. In the illustrativeexample, device 232 is a hardware component that uses electrical power.For example, device 232 may be selected from one of a line replaceableunit, a light, an organic light emitting diode display panel, anelectromechanical switch, a smart glass window, or some other suitablecomponent.

Device 232 may be located in panel 210, another panel, or in some othersuitable location. For example, device 232 may be a light integratedinto panel 210 that forms part of a wall. In another illustrativeexample, device 232 may be an electromechanical switch integrated intopanel 210 as part of a stowage bin for aircraft 204.

Further, power system 234 may also be electrically connected to battery224. Power system 234 functions to charge battery 224. Power system 234may take various forms. For example, power system 234 may be selectedfrom at least one of an energy harvesting system, a battery, anauxiliary power source, or some other suitable type of power source.

When power system 234 takes the form of an energy harvesting system, theenergy harvesting system may use various mechanisms to generate energy.For example, the energy harvesting system may be selected from at leastone of a solar cell, a thermoelectric generator, a micro wind turbine,or some other suitable mechanism.

In the illustrative example, dielectric core 212 acts as an insulatorbetween first conductive adhesive 220 and second conductive adhesive226. In other words, the materials and structure of dielectric core 212are such that a current does not flow between first conductive adhesive220 and second conductive adhesive 226 through dielectric core 212.

With reference next to FIG. 3, an illustration of a block diagram of apanel is depicted in accordance with an illustrative embodiment. In theillustrative examples, the same reference numeral may be used in morethan one figure. This reuse of a reference numeral in different figuresrepresents the same element in the different figures.

In this figure, a more detailed illustration of panel 210 in FIG. 2 isshown. As depicted, dielectric core 212 may take different forms. Forexample, dielectric core 212 may be honeycomb core 300, solid core 302,hybrid core 304, or take some other suitable form.

Honeycomb core 300 is a structure having a volume and a shape that isselected based on the use for panel 210. For example, honeycomb core 300may have a shape selected from one of flat, curved, contoured, or someother suitable shape. For example, a flat shape may be used for a dooror a wall. A curved shape may be used for a stowage bin or some othersimilar structure. Honeycomb core 300 is selected to have structuralrigidity and resistance to changes of at least one of the shape or thevolume based on the use for panel 210.

Honeycomb core 300 is comprised of an array of cellular hollow cells. Inthe illustrative example, honeycomb core 300 may have cells that arecolumnar and hexagonal in shape. The materials used may be selected suchthat honeycomb core 300 functions as an electrical insulator. Forexample, the materials may be selected from at least one of a metallicmaterial, a nonmetallic material, an alloy, a composite, cardboard,phenolic resin coated paper, a plastic material, fiberglass, or othersuitable materials. When materials in honeycomb core 300 are conductive,facesheets may be used on either side of honeycomb core 300 that arenonconductive in a manner that causes honeycomb core 300 to function asan electrical insulator when combined with the facesheets. In thismanner, honeycomb core 300 may function as an electrical insulator whencombined with the facesheets. Other types of dielectric core 212, suchas solid core 302 and hybrid core 304, also may be configured tofunction as an electrical insulator using facesheets or in some othersuitable manner.

Honeycomb core 300 may be used to reduce the amount of material in panel210. In this manner, the weight of panel 210 may be reduced whilemaintaining or increasing the structural composite properties ofhoneycomb core 300. With the use of honeycomb core 300, the weight ofpanel 210 may be reduced as compared to using other types of cores.

Solid core 302 is a structure that is comprised of a single material ina solid layer. Solid core 302 may be selected to have a volume and ashape with structural rigidity and resistance to changes of at least oneof the shape or the volume based on the use for panel 210.

The material for solid core 302 is selected such that solid core 302functions as an electrical insulator. For example, solid core 302 may becomprised of a metallic material, a non-metallic material, a plasticmaterial, an alloy, a composite material, a polycarbonate, or some othersuitable type of material. Facesheets that have insulative propertiesmay be used when the material in solid core 302 is conductive such thatsolid core 302 with the facesheets functions as an electrical insulator.Using solid core 302 may be desirable when panel 210 is part of astructure with detailed parts or components that protrude or extendbeyond any of a flat, curved, or contoured surface.

In the illustrative example, hybrid core 304 is a structure that has avolume and a shape with structural rigidity and resistance to changes ofat least one of the shape or the volume based on the use for panel 210.Hybrid core 304 is formed from a combination of materials. The selectionof the materials is such that hybrid core 304 functions as an electricalinsulator.

For example, hybrid core 304 may be selected from a combination of twoor more of a metallic material, a non-metallic material, an alloy, acomposite material, a plastic material, or some combination of these orother materials. For example, the material in hybrid core 304 may be ametal infused plastic. Facesheets that have insulative properties may beused when the material in hybrid core 304 is conductive such that hybridcore 304 with the facesheets functions as an electrical insulator.

In the illustrative example, hybrid core 304 may be formed from multiplelayers. The different layers may be comprised of different materials.These different layers in hybrid core 304 may have different densitiesin the illustrative example.

Further, hybrid core 304 may be a single layer of material that hasfeatures located within a layer of material. These features may be, forexample, voids or cells. In one illustrative example, hybrid core 304may be a plastic foam, a polycarbonate with cells, or some othersuitable form. In another illustrative example, hybrid core 304 may be asingle layer that is modified at a molecular-level to change materialproperties to reduce the weight of hybrid core 304.

Using hybrid core 304 may be desirable when panel 210 is part of astructure with detailed parts or components that protrude or extendbeyond any of a flat, curved, or contoured surface. The weight of hybridcore 304 may be less than using solid core 302 with the same volume andsize.

As depicted, a number of first sheets 306 are attached to first side 236of dielectric core 212. A number of second sheets 308 are attached tosecond side 238 of dielectric core 212. In this illustrative example,the number of first sheets 306 includes first sheet 214. The number ofsecond sheets 308 includes second sheet 216.

The number of first sheets 306 may include one or more other sheets inaddition to first sheet 214. In a similar manner, the number of secondsheets 308 may also include one or more other sheets in addition tosecond sheet 216. For example, depending on what other sheets arepresent in the number of first sheets 306 and the number of secondsheets 308, first sheet 214 and second sheet 216 may be selected fromone of an inner sheet, an outer sheet, a laminate, a decorativelaminate, a composite layer, or some other suitable type of sheet.

For example, first sheet 214 may be facesheet 310 on first side 236 ofdielectric core 212, and second sheet 216 may be facesheet 312 on secondside 238 of dielectric core 212. With this type of configuration, thenumber of first sheets 306 also may include first inner sheet 314 andthe number of second sheets 308 may include second inner sheet 316.First inner sheet 314 is located between facesheet 310 and dielectriccore 212, and second inner sheet 316 is located between facesheet 312and dielectric core 212.

In yet another example, the adhesive on a sheet may not all be comprisedof a conductive adhesive. Instead, a combination of areas of conductiveadhesive and nonconductive adhesive may be used. The regions may beformed through various techniques, such as screen printing or serigraphprinting. The amount of conductive adhesive may depend on the voltagedesired to be generated. Additionally, if the amount of power can besupplied to a smaller area of conductive adhesive forming a battery thanall of the panel, that smaller area may be used to reduce the amount ofheat generated.

The illustration of battery environment 200 and the different componentsin battery environment 200 in FIG. 2 and FIG. 3 are not meant to implyphysical or architectural limitations to the manner in which anillustrative embodiment may be implemented. Other components in additionto or in place of the ones illustrated may be used. Some components maybe unnecessary. Also, the blocks are presented to illustrate somefunctional components. One or more of these blocks may be combined,divided, or combined and divided into different blocks when implementedin an illustrative embodiment.

Although the illustrative example in FIG. 1 is described with respect toplatform 202 in the form of aircraft 204, other illustrative examplesmay be applied to other types of platforms. For example, platform 202may be a mobile platform, a stationary platform, a land-based structure,an aquatic-based structure, or a space-based structure. Morespecifically, the platform may be a surface ship, a tank, a personnelcarrier, a train, a spacecraft, a space station, a satellite, asubmarine, an automobile, a power plant, a bridge, a theater, a house, amanufacturing facility, a building, or other suitable platforms.

As another example, panel 210 may have one or more devices in additionto device 232. For example, panel 210 may include an electromechanicallatch as a first device and an organic light emitting diode display as asecond device. As yet another example, additional layers of conductiveadhesives may be added to form additional electrodes for one or morebatteries in addition to the battery formed by first conductive adhesive220, second conductive adhesive 226, and dielectric insulator 230.

FIGS. 4-6 are illustrations of some implementations for panel 210 shownin block form in FIG. 2 and FIG. 3. With reference first to FIG. 4, anillustration of a panel is depicted in accordance with an illustrativeembodiment. As depicted, panel 400 is an example of one implementationof panel 210.

In this illustrative example, panel 400 includes honeycomb core 402,inner sheet 404, inner sheet 406, outer sheet 408, and decorativelaminate 410. Outer sheet 408 has conductive adhesive 412, anddecorative laminate 410 has conductive adhesive 414.

Honeycomb core 402 is an example of an implementation of honeycomb core300 shown in block form in FIG. 3. Outer sheet 408 is an example of animplementation of first sheet 214, and decorative laminate 410 is anexample of an implementation of second sheet 216 shown in block form inFIG. 2 and FIG. 3. Conductive adhesive 412 is an example of animplementation of first conductive adhesive 220, and conductive adhesive414 is an example of an implementation for second conductive adhesive226 shown in block form in FIG. 2 and FIG. 3.

In this illustrative example, honeycomb core 402 may be constructed fromcardboard, plastic, or some other suitable material. Inner sheet 404 andinner sheet 406 may each be made of one or more layers of compositematerials.

For example, inner sheet 404 and inner sheet 406 each may be comprisedof a number of layers of fabric that are impregnated with a resin. Thefabric may, for example, be formed from a fiber made of at least one offiberglass, carbon, graphite, a para-aramid synthetic fiber, or someother suitable type of material.

As depicted, honeycomb core 402 is constructed to function as adielectric insulator. Conductive adhesive 412 forms a first electrode,and conductive adhesive 414 forms a second electrode. In this manner,panel 400 also functions as a battery in addition to a structuralcomponent.

The construction of panel 400 does not require additional layers ofmaterials. Conductive adhesive 412 and conductive adhesive 414 are usedin place of adhesives normally used for a panel.

Turning next to FIG. 5, an illustration of a panel with a device isdepicted in accordance with an illustrative embodiment. In thisillustrative example, panel 500 is an example of one implementation ofpanel 210 shown in block form in FIG. 2 and FIG. 3. Electromechanicallatch 502 is an example of an implementation of device 232 shown inblock form in FIG. 2.

In this illustrative example, panel 500 is a door for a cabinet.Electromechanical latch 502 may operate to lock and unlock the doorformed by panel 500. Additionally, electromechanical latch 502 alsoincludes light 504.

In this illustrative example, panel 500 supplies electrical power toelectromechanical latch 502. For example, panel 500 may supplyelectrical current to electromechanical latch 502. The current issupplied using a battery integrated as part of panel 500.

Turning next to FIG. 6, an illustration of a cross-sectional view of apanel with a device is depicted in accordance with an illustrativeembodiment. In this depicted example, a cross-sectional view of panel500 is shown taken along lines 6-6 in FIG. 5.

In this illustrative example, panel 500 includes honeycomb core 600. Asdepicted, honeycomb core 600 is constructed in a manner to function as adielectric insulator.

Panel 500 also includes inner sheet 602, inner sheet 604, inner sheet606, inner sheet 608, decorative laminate 610, and decorative laminate612. Panel 500 also includes adhesive 614, adhesive 616, conductiveadhesive 618, conductive adhesive 620, conductive adhesive 622, andconductive adhesive 624.

As depicted, adhesive 614 is located between inner sheet 602 andhoneycomb core 600 and attaches inner sheet 602 to honeycomb core 600.Adhesive 616 is located between inner sheet 604 and honeycomb core 600.Adhesive 616 attaches inner sheet 604 to honeycomb core 600.

In the illustrative example, conductive adhesive 618 is located betweeninner sheet 602 and inner sheet 606. Conductive adhesive 618 attachesinner sheet 606 to inner sheet 602. Conductive adhesive 620 is locatedbetween inner sheet 604 and inner sheet 608. Conductive adhesive 620attaches inner sheet 608 to inner sheet 604.

Conductive adhesive 622 is located between inner sheet 606 anddecorative laminate 610. Conductive adhesive 622 attaches decorativelaminate 610 to inner sheet 606. Conductive adhesive 624 is locatedbetween inner sheet 608 and decorative laminate 612. Conductive adhesive624 attaches decorative laminate 612 to inner sheet 608.

In this view, electromechanical latch 502 has contact 626, contact 628,contact 630, and contact 632. These contacts electrically connectelectromechanical latch 502 and light 504 to conductive adhesive 622,conductive adhesive 618, conductive adhesive 620, and conductiveadhesive 624.

As depicted, conductive adhesive 618 and conductive adhesive 620 form afirst set of electrodes for a first battery, while conductive adhesive622 and conductive adhesive 624 form a second set of electrodes for asecond battery. For example, the first battery may operateelectromechanical latch 502, while the second battery may provide powerto operate light 504.

The illustration of panels with integrated batteries in FIGS. 4-6 areprovided as examples of some implementations of panel 210 shown in blockform in FIG. 2 and FIG. 3. These illustrations are not meant to limitthe manner in which other illustrative examples may be implemented.

For example, panel 400 in FIG. 4 and panel 500 in FIG. 5 are examples ofimplementations of panel 210 that are shown as being substantiallyplanar. In other illustrative examples, a panel may have other shapes.For example, the panel may be curved, angled, or have some othersuitable shape. Further, the panel also may include protrusions,indentations, groups, or other features in other illustrative examples.

FIGS. 7-9 are illustrations of parts in which panels may be used. Thesefigures show examples of how panel 210 for use in parts 206, shown inblock form in FIG. 2 in FIG. 3, may be implemented.

With reference to FIG. 7, an illustration of a composite panel used in awall in an aircraft is depicted in accordance with an illustrativeembodiment. As depicted, composite panel 700 is part of the wall forlavatory 702 inside the interior of an aircraft. As depicted in thisillustrative example, composite panel 700 includes light 704. Compositepanel 700 also includes an integrated battery (not shown) that providespower to operate light 704 and may have components similar to those inpanel 210 shown in block form in FIG. 2 and FIG. 3.

Turning next to FIG. 8, an illustration of a composite panel used in astorage in an aircraft is depicted in accordance with an illustrativeembodiment. As depicted, composite panel 800 is part of stowage bin 802in the interior of an aircraft. In this example, composite panel 800includes electromechanical latch 804 for stowage bin 802. Compositepanel 800 includes an integrated battery (not shown) that provides powerto operate electromechanical latch 804 and may have components similarto those in panel 210 shown in block form in FIG. 2 and FIG. 3.

With reference now to FIG. 9, an illustration of a composite panel usedin a wall in an aircraft is depicted in accordance with an illustrativeembodiment. In this illustrative example, composite panel 900 is part ofthe wall for fuselage 902 of an aircraft. As depicted in thisillustrative example, composite panel 900 includes signage 904.Composite panel 900 also includes an integrated battery (not shown) thatprovides power to light up signage 904 and may have components similarto those in panel 210 in FIG. 2 and FIG. 3.

The illustration of the composite panels and devices in FIGS. 7-9 areprovided only for purposes of illustrating one manner in which panel 210and device 232, shown in block form in FIG. 2 and FIG. 3, may beimplemented. These illustrations are not meant to limit the manner inwhich other illustrative examples may implement panel 210 and device232.

For example, a panel may only supply power and not include the device.The panel may include an integrated battery similar to the configurationof panel 210 in FIG. 2 and FIG. 3. This battery is integrated as part ofthe panel and may be connected to a device in another panel, dependingupon the particular implementation.

In yet another illustrative example, at least one of the panel or thedevice may be used on the exterior of an aircraft. For example, thepanel may be used to form a composite skin panel for the aircraft. Thedevice may be a light or other device that uses power from the compositeskin.

In still other illustrative examples, the panel with the device may beimplemented in other types of platforms in addition to an aircraft. Forexample, a panel may be used to form a wall in the hallway of abuilding. A device in the form of a light may be located in the panelwall.

Turning next to FIG. 10, an illustration of a flowchart of a process forsupplying electrical current to a device is depicted in accordance withan illustrative embodiment. The process illustrated in FIG. 10 may beimplemented in battery environment 200 in FIG. 2. For example, theprocess may be implemented using composite panel 218 in FIG. 2.

The process begins by sending an electrical current into a device from apanel (operation 1000). In operation 1000, the panel may be implementedusing panel 210 shown in block form in FIG. 2 and FIG. 3. The panel hasa dielectric core; a first sheet with a first conductive adhesiveattaching the first sheet to a first side of the dielectric core,wherein the first conductive adhesive is a first electrode for abattery; a second sheet with a second conductive adhesive attaching thesecond sheet to a second side of the dielectric core, wherein the secondconductive adhesive is a second electrode for the battery.

In this example, the device may be part of the panel. In other examples,the device may be in another panel or location.

The process operates the device using the electrical current from thebattery in the panel (operation 1002). The process terminatesthereafter.

The flowchart and block diagrams in the different depicted embodimentsillustrate the architecture, functionality, and operation of somepossible implementations of apparatuses and methods in an illustrativeembodiment. In this regard, each block in the flowchart or blockdiagrams may represent at least one of a module, a segment, a function,or a portion of an operation or step. Each block in the flowchart or theblock diagrams may be implemented using special purpose hardware systemsthat perform the different operations or combinations of special purposehardware and program code run by the special purpose hardware.

In some alternative implementations of an illustrative embodiment, thefunction or functions noted in the blocks may occur out of the ordernoted in the figures. For example, in some cases, two blocks shown insuccession may be performed substantially concurrently, or the blocksmay sometimes be performed in the reverse order, depending upon thefunctionality involved. Also, other blocks may be added in addition tothe illustrated blocks in a flowchart or block diagram.

The illustrative embodiments of the present disclosure may be describedin the context of aircraft manufacturing and service method 1100 asshown in FIG. 11 and aircraft 1200 as shown in FIG. 12. Turning first toFIG. 11, an illustration of a block diagram of an aircraft manufacturingand service method is depicted in accordance with an illustrativeembodiment. During pre-production, aircraft manufacturing and servicemethod 1100 may include specification and design 1102 of aircraft 1200in FIG. 12 and material procurement 1104.

During production, component and subassembly manufacturing 1106 andsystem integration 1108 of aircraft 1200 in FIG. 12 takes place.Thereafter, aircraft 1200 may go through certification and delivery 1110in order to be placed in service 1112. While in service 1112 by acustomer, aircraft 1200 is scheduled for routine maintenance and service1114, which may include modification, reconfiguration, refurbishment,and other maintenance or service.

Each of the processes of aircraft manufacturing and service method 1100may be performed or carried out by a system integrator, a third party,an operator, or some combination thereof. In these examples, theoperator may be a customer. For the purposes of this description, asystem integrator may include, without limitation, any number ofaircraft manufacturers and major-system subcontractors; a third partymay include, without limitation, any number of vendors, subcontractors,and suppliers; and an operator may be an airline, a leasing company, amilitary entity, a service organization, and so on.

With reference now to FIG. 12, an illustration of a block diagram of anaircraft is depicted in which an illustrative embodiment may beimplemented. In this example, aircraft 1200 is produced by aircraftmanufacturing and service method 1100 in FIG. 11 and may includeairframe 1202 with plurality of systems 1204 and interior 1206. Examplesof systems 1204 include one or more of propulsion system 1208,electrical system 1210, hydraulic system 1212, and environmental system1214. Any number of other systems may be included. Although an aerospaceexample is shown, different illustrative embodiments may be applied toother industries, such as the automotive industry. Apparatuses andmethods embodied herein may be employed during at least one of thestages of aircraft manufacturing and service method 1100 in FIG. 11.

In one illustrative example, components or subassemblies produced incomponent and subassembly manufacturing 1106 in FIG. 11 may befabricated or manufactured in a manner similar to components orsubassemblies produced while aircraft 1200 is in service 1112 in FIG.11. For example, a panel containing an integrated battery, such as panel210 shown in block form in FIG. 2 and FIG. 3, may be manufactured duringany of these different stages of aircraft manufacturing and servicemethod 1100 in aircraft 1200.

As yet another example, one or more apparatus embodiments, methodembodiments, or a combination thereof may be utilized during productionstages, such as component and subassembly manufacturing 1106 and systemintegration 1108 in FIG. 11. One or more apparatus embodiments, methodembodiments, or a combination thereof may be utilized while aircraft1200 is in service 1112, during maintenance and service 1114 in FIG. 11,or both.

For example, panel 210 shown in block form in FIG. 2 and FIG. 3 may bemanufactured to replace a panel or refurbishment of aircraft 1200 duringmaintenance and service 1114. As another example, panel 210 ismanufactured during component and subassembly manufacturing 1106 tomanufacture aircraft 1200. When installed in aircraft 1200, panel 210may operate to supply power in the form of electrical current while inservice 1112.

The use of a number of the different illustrative embodiments maysubstantially expedite the assembly of aircraft 1200, reduce the cost ofaircraft 1200, or both expedite the assembly of aircraft 1200 and reducethe cost of aircraft 1200. For example, the use of panel 210, shown inblock form in FIG. 2 and FIG. 3, reduces wiring that may be needed toconnect devices to the power system in aircraft 1200. Additionally, theuse of panel 210 also may decrease the need of an upgraded power systemor additional power supplies within the power system.

As a result, at least one of weight, manufacturing time, or complexityof manufacturing of aircraft 1200 may be reduced. As a result, one ormore of the technical solutions described herein overcome a technicalproblem with providing power to devices associated with panels in anaircraft.

The description of the different illustrative embodiments has beenpresented for purposes of illustration and description and is notintended to be exhaustive or limited to the embodiments in the formdisclosed. The different illustrative examples describe components thatperform actions or operations. In an illustrative embodiment, acomponent may be configured to perform the action or operationdescribed. For example, the component may have a configuration or designfor a structure that provides the component an ability to perform theaction or operation that is described in the illustrative examples asbeing performed by the component.

Many modifications and variations will be apparent to those of ordinaryskill in the art. Further, different illustrative embodiments mayprovide different features as compared to other desirable embodiments.The embodiment or embodiments selected are chosen and described in orderto best explain the principles of the embodiments, the practicalapplication, and to enable others of ordinary skill in the art tounderstand the disclosure for various embodiments with variousmodifications as are suited to the particular use contemplated.

What is claimed is:
 1. A panel containing an integrated battery,comprising: a dielectric core; a first sheet; a first conductiveadhesive attaching the first sheet to a first side of the dielectriccore, wherein the first conductive adhesive is a first electrode for thebattery; a second sheet; a second conductive adhesive attaching thesecond sheet to a second side of the dielectric core, wherein the secondconductive adhesive is a second electrode for the battery; wherein thedielectric core, the first sheet, and the second sheet form the panel;and wherein the panel comprises a structural component of a part.
 2. Thepanel containing the integrated battery of claim 1, wherein the partcomprises a part of an aircraft.
 3. The panel containing the integratedbattery of claim 1, wherein the part is selected from one of an interiorwall, a ceiling, an overhead stowage bin, a door, a closet, a sidewall,a partition, and a floor.
 4. The panel containing the integrated batteryof claim 1, wherein the first sheet and the second sheet comprise anumber of layers of a composite material.
 5. The panel containing theintegrated battery of claim 1, wherein the second sheet comprises adecorative laminate.
 6. The panel containing the integrated battery ofclaim 1 further comprising: a device that uses electrical power mountedin the panel and electrically connected to the first electrode and tothe second electrode to supply the electrical power from the battery tothe device.
 7. The panel containing the integrated battery of claim 6,wherein the device is selected from one of a line replaceable unit, alight, an organic light emitting diode display panel, anelectromechanical latch, and a smart glass window.
 8. A panel containingan integrated battery, comprising: a dielectric core; a first sheet; afirst conductive adhesive attaching the first sheet to a first side ofthe dielectric core, wherein the first conductive adhesive is a firstelectrode for the battery; a second sheet; a second conductive adhesiveattaching the second sheet to a second side of the dielectric core,wherein the second conductive adhesive is a second electrode for thebattery; wherein the dielectric core, the first sheet, and the secondsheet form the panel; and a device that uses electrical power mounted inthe panel and electrically connected to the first electrode and to thesecond electrode to supply the electrical power from the battery to thedevice.
 9. The panel containing the integrated battery of claim 8,wherein the panel comprises a structural component of a part of anaircraft.
 10. The panel containing the integrated battery of claim 8,wherein the panel comprises a structural component of a part selectedfrom one of an interior wall, a ceiling, an overhead stowage bin, adoor, a closet, a sidewall, a partition, and a floor.
 11. The panelcontaining the integrated battery of claim 8, wherein the first sheetand the second sheet comprise a number of layers of a compositematerial.
 12. The panel containing the integrated battery of claim 8,wherein the second sheet comprises a decorative laminate.
 13. The panelcontaining the integrated battery of claim 8, wherein the device isselected from one of a line replaceable unit, a light, an organic lightemitting diode display panel, an electromechanical latch, and a smartglass window.
 14. A method for supplying an electrical current, themethod comprising: sending the electrical current into a device from apanel containing an integrated battery, wherein the panel comprises: adielectric core, a first sheet, a first conductive adhesive attachingthe first sheet to a first side of the dielectric core, wherein thefirst conductive adhesive is a first electrode for the battery, a secondsheet, and a second conductive adhesive attaching the second sheet to asecond side of the dielectric core, wherein the second conductiveadhesive is a second electrode for the battery; wherein the dielectriccore, the first sheet, and the second sheet form the panel; wherein thepanel comprises a structural component of a part; and operating thedevice using the electrical current from the battery in the panel. 15.The method of claim 14, wherein the part comprises a part of anaircraft.
 16. The method of claim 14, wherein the part is selected fromone of an interior wall, a ceiling, an overhead stowage bin, a door, acloset, a sidewall, a partition, and a floor.
 17. The method of claim14, wherein the first sheet and the second sheet comprise a number oflayers of a composite material.
 18. The method of claim 14, wherein thesecond sheet comprises a decorative laminate.
 19. The method of claim14, wherein the device is mounted in the panel and electricallyconnected to the first electrode and to the second electrode to supplythe electrical current from the battery to the device.
 20. The method ofclaim 19, wherein the device is selected from one of a line replaceableunit, a light, an organic light emitting diode display panel, anelectromechanical latch, and a smart glass window.